Lightweight rammer

ABSTRACT

A lightweight rammer system and method for engaging an artillery projectile or propellant charge, wherein the rammer system comprises an internal combustion generator comprising a first firing mechanism; an actuator driven by the firing mechanism, wherein the actuator comprises a propellant combustible into a pressurized fluid; and a pressure accumulator connected to the actuator, wherein the pressure accumulator controllably releases the pressurized fluid; a ramming component connected to the internal combustion generator and powered by the pressurized fluid; and means for regenerating pressure in the pressure accumulator actuated by recoil motion of the ramming component.

GOVERNMENT INTEREST

The invention described herein may be manufactured, used, and/orlicensed by or for the United States Government.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The invention generally relates to rammers used for artilleryprojectiles, and more particularly to a self-powered rammer for engagingartillery projectiles or propellant charges.

2. Description of the Related Art

Projectiles, and when separate from projectiles, the propellant charges,must be thrust far enough into the tube of an artillery piece for properloading. In some instances, in order to properly load a projectile,man-powered rammers are used. In other instances, artillery withauxiliary power such as the South African G-5 may be used to power therammers. The former Soviet 2A36 and 2A65 towed artillery pieces use arammer. The rammer and breech of the 2A36 are operated from a hydraulicreservoir charged by recoil, but until the first shot, the rammer forthe 2A36 is initially manually operated. The rammer for the 2A65 uses aspring assisted mechanism. However, these types of towed artillerypieces are extremely heavy, and may not be suitable for air transport.

Self-propelled artillery uses powered rammers which are hydraulicallyactuated. Typically, hydraulic power is used in order to satisfy therequirement for a very rapid exertion of force with a very high force atthe same time that the actuating devices are moving at a high speed.Electric motors exert a maximum torque at zero speed with the torquefalling off as the motor speed increases. This phenomenon is generallyunavoidable due to the generation of counter electromagnetic forcescaused by a turning motor as verified by Lenz' law. Internal combustionengines cannot cease to turn without stopping completely (stalling),which requires clutches or hydro-pumped transmissions to exertintermittent forces. However, these additional components tend to addextra weight and complexity to the system.

Furthermore, in the past, some heavy naval turret artillery used steampowered rammers. Here, steam from the ship's boilers was used to powerthe rammers. However, these components tended to be quite heavy and fuelintensive. Therefore, there remains a need for a lightweightself-propelled rammer which does not require heavy sub-components orpower sources or laborious and slow manual pumping to propel the rammerfor engaging an artillery projectile or propellant charge.

SUMMARY OF THE INVENTION

In view of the foregoing, an embodiment of the invention provides arammer system and an artillery ramming assembly for engaging anartillery projectile or propellant charge, wherein the rammer systemcomprises an internal combustion generator comprising a first firingmechanism; an actuator driven by the firing mechanism, wherein theactuator comprises a propellant combustible or decomposable into apressurized fluid; and a pressure accumulator connected to the actuator,wherein the pressure accumulator controllably releases the pressurizedfluid; a ramming component connected to the internal combustiongenerator and powered by the pressurized fluid; and means forregenerating pressure in the pressure accumulator actuated by recoilmotion of the ramming component.

According to the invention, the first firing mechanism comprises any ofa catalyst, a spark-generating mechanism, and a percussion or electricinitiation-firing pin or probe. In one embodiment, the actuatorcomprises a combustion chamber configured for allowing the propellant tocombust upon actuation from the first firing mechanism; and a firstrupture disc connected to the combustion chamber, wherein the actuatorfurther comprises at least one hole configured in the actuator andpositioned between the combustion chamber and the first rupture disc; apressure reservoir adjacent to the first rupture disc; and a particulatefilter adjacent to the pressure reservoir.

In an another embodiment, the actuator further comprises a pressurereservoir connected to the first rupture disc; a second rupture disc; aplurality of holes configured in the actuator and positioned between thepressure reservoir and the second rupture disc; and a pneumatic chamberadjacent to the second rupture disc. The actuator further comprises aslidably mounted closure wedge connected to the pneumatic chamber.Additionally, in one aspect of the invention, the actuator furthercomprises a particulate filter adjacent to the pneumatic chamber. Inanother aspect of the invention, the actuator comprises a combustionchamber configured for allowing the propellant to combust upon actuationfrom the first firing mechanism; a second firing mechanism; and a chargetube connecting the first firing mechanism to the second firingmechanism.

Moreover, the propellant comprises any of a solid propellant, a liquidpropellant, a fluid propellant, and a combination thereof. Also,according to another embodiment, the propellant comprises amonopropellant mixture comprising a liquid monopropellant and acatalyst. The pressure accumulator comprises a first orifice connectedto the actuator; a piston; a pressure release valve; a second orificeseparated from the first orifice by the piston, wherein the secondorifice being configured to have a height smaller than a height of thepressure accumulator; a tube portion connected to the second orifice;and a fluid release valve disposed in the tube portion. The systemfurther comprises a particulate filter disposed in the tube portion.

Furthermore, the ramming component comprises a rammer chamber connectedto the tube portion; a rammer piston enclosed in a portion of the rammerchamber; at least one bias member connecting the rammer piston to therammer chamber; a pressure vent disposed in the rammer chamber; and anopening in the rammer chamber configured for allowing translation of therammer piston therebetween, wherein the ramming component furthercomprises a seal configured in the opening and positioned proximate tothe rammer piston. Additionally, the rammer piston comprises a generallyelongated cylindrical shaft portion and a pair of generally cylindricalend portions positioned on opposite ends of the shaft portion.

Another embodiment of the invention provides an artillery ramming systemcomprising means for triggering combustion of a combustible propellantinto a fluid; means for pressurizing the fluid; means for controlling aflow of the pressurized fluid; means, powered by the pressurized fluid,for ramming any of an artillery projectile and propellant charge; andmeans, actuated by recoil motion of the means for ramming, forregenerating pressure in the artillery ramming system.

Another aspect of the invention provides a method of ramming anartillery projectile or propellant charge, wherein the method comprisestriggering combustion of a combustible propellant into a fluid;pressurizing the fluid in a pressure vessel; controlling a flow of thepressurized fluid in a pressure accumulator; ramming any of an artilleryprojectile and propellant charge using a rammer driven by powergenerated by the pressurized fluid; and regenerating pressure in thepressure accumulator using recoil motion of the rammer, wherein thetriggering occurs using a firing mechanism comprising any of a catalyst,a spark-generating mechanism, and a percussion or electricinitiation-firing pin or probe, wherein in the step of triggering, thecombustible propellant comprises any of a solid propellant, a liquidpropellant, a fluid propellant, and a combination thereof, and whereinthe combustible propellant comprises a monopropellant mixture comprisinga liquid monopropellant and a catalyst.

The embodiments of the invention provide a rammer system that issufficiently lightweight to be dismountable and transported separatelyfrom other artillery pieces to save weight when sling loading, ifnecessary. Because there are no hydraulic reservoirs or motors on therammer system, the rammer system could slip over studs on the carriageof a gun, perhaps engaging the recoil mass by a pad, could be removable,and could be lifted by as few as two crewmen. Other advantages affordedby the embodiments of the invention are increased speed, reducedfatigue, reduced heat stress when wearing chemical protective gear,especially overgarments, reduced personnel requirements, and increasedsafety.

These and other aspects of the embodiments of the invention will bebetter appreciated and understood when considered in conjunction withthe following description and the accompanying drawings. It should beunderstood, however, that the following descriptions, while indicatingpreferred embodiments of the invention and numerous specific detailsthereof, are given by way of illustration and not of limitation. Manychanges and modifications may be made within the scope of theembodiments of the invention without departing from the spirit thereof,and the embodiments of the invention include all such modifications.

BRIEF DESCRIPTION OF THE DRAWINGS

The embodiments of the invention will be better understood from thefollowing detailed description with reference to the drawings, in which:

FIG. 1 is a cross-sectional schematic diagram of a rammer systemaccording to a first embodiment of the invention;

FIG. 2 is a cross-sectional schematic diagram of a rammer systemaccording to a second embodiment of the invention;

FIG. 3 is a cross-sectional schematic diagram of a rammer systemaccording to a third embodiment of the invention;

FIGS. 4 through 7 are cross-sectional schematic diagrams of aregeneration rammer system during successive stages of operationaccording to a fourth embodiment of the invention;

FIG. 8( a) is an isolated view of the actuator component of FIGS. 1through 7 according to a first embodiment of the invention;

FIG. 8( b) is an isolated view of the actuator component of FIGS. 1through 7 according to a second embodiment of the invention;

FIG. 8( c) is an isolated view of the actuator component of FIGS. 1through 7 according to a third embodiment of the invention;

FIG. 8( d) is an isolated view of the actuator component of FIGS. 1through 7 according to a fourth embodiment of the invention;

FIG. 8( e) is an isolated view of the actuator component of FIGS. 1through 7 according to a fifth embodiment of the invention; and

FIG. 9 is a flow diagram illustrating a preferred method of anembodiment of the invention.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS OF THE INVENTION

The embodiments of the invention and the various features andadvantageous details thereof are explained more fully with reference tothe non-limiting embodiments that are illustrated in the accompanyingdrawings and detailed in the following description. It should be notedthat the features illustrated in the drawings are not necessarily drawnto scale. Descriptions of well-known components and processingtechniques are omitted so as to not unnecessarily obscure theembodiments of the invention. The examples used herein are intendedmerely to facilitate an understanding of ways in which the embodimentsof the invention may be practiced and to further enable those of skillin the art to practice the embodiments of the invention. Accordingly,the examples should not be construed as limiting the scope of theembodiments of the invention.

As previously mentioned, there remains a need for a lightweightself-powered rammer which does not require heavy sub-components or powersources or laborious and slow manual pumping to propel the rammer forengaging an artillery projectile or propellant charge (such asgunpowder). The embodiments of the invention achieve this by using a gasgenerator producing high pressure gas, which acts directly or through afloating piston on another piston that performs the motions of rammingthe artillery. Referring now to the drawings, and more particularly toFIGS. 1 through 9, there are shown preferred embodiments of theinvention.

According to the embodiments of the invention, the rammer systemoperates by use of a pressure accumulator 19 for the loading of eachshot (illustrated in FIGS. 1 through 3), or by initial pressurization ofthe actuator component 14, and then regeneration of the pressure byharnessing the recoil motion of the gun (illustrated in FIGS. 4 through7). The merit of regeneration is the decrease in the consumables used(the gas generators for the subsequent rounds), and the merit of theloading of each shot is the exchange of use of lightweight gasgenerators instead of heavier regeneration components. Depending on thedesign goal of the gun designer, weight may be profitably traded offversus consumables. Another merit of the use of regeneration withpressurization immediately prior to ramming is that much of the pressurefrom the actuator component 14 will initially be derived from thetemperature of the gas contained therein. If the gas is allowed to sitquiescently between shots, the temperature and, hence, pressure may dropbelow the requisite for ramming. As such, venting of the pressureaccumulator 19 and subsequent re-pressurization from a new actuatorcomponent 14 may be desirable.

FIG. 1 illustrates an open cycle rammer system 1 according to a firstembodiment of the invention, whereby the open cycle rammer system 1utilizes a source of working pressure and preferably uses an actuatingfluid (gas or liquid) 22, but does not require external power supplies,motors, etc. Generally, the rammer system 1 comprises an internalcombustion or monopropellant generator component 2 connected to aramming component 3. More particularly, the rammer system 1 comprises anouter casing 24 which houses several sub-components. Thesesub-components include a firing mechanism 5, which is preferablyembodied as a primer, catalyst, spark, or percussion or electricinitiation-firing pin or probe.

The firing mechanism 5 engages a breech closure 12, which is preferablyembodied as a horizontally guided sliding wedge. The breech closure 12connects to a first side of an actuator component 14, wherein theactuator component 14 is embodied as a combustion chamber, a propellantcartridge, or a pressure vessel. The rammer system 1 includes a pressureaccumulator 19 on a second side of the actuator component 14, whereinthe pressure accumulator 19 generally includes buffered space 16configured for allowing variable pressure inside the pressureaccumulator 19. The pressure accumulator 19 is particularly useful formetering rapidly produced high pressure gas 60 (shown in FIGS. 4 through7) formed in the actuator component 14, wherein the high pressure gas 60generally fills the area afforded by the buffered space 16 in thepressure accumulator 19. For simplicity, FIG. 1 does not illustrate thehigh pressure gas 60 in order to not unnecessarily obscure the othervisible components of the rammer system 1. Furthermore, the pressureaccumulator 19 is desirable for separately loading ammunition where tworammer strokes are required. A vent 21 connecting to a valve 20 isconnected to the pressure accumulator 19 to help release accumulatedpressure within the pressure accumulator 19.

A piston 18, which may be embodied as a floating piston or aspring-loaded piston, is aligned in the pressure accumulator 19 to helpdrive the actuating fluid 22 located in the pressure accumulator 19. Thegas 60 generated in the actuator component 14 and pressurized in thepressure accumulator 19 drives the piston 18, which then drives theactuating fluid 22 (best seen in FIG. 4). In a spring-loaded embodiment,the piston 18 may use a spring (not shown) or a compressible gas 60,wherein the initializing gas 60 may act as the spring. The compressionof piston 18 can be used to pressurize the actuating fluid 22 in thepressure accumulator 19. The generator component 2 may vent gas 60(using vent 21) to aid in relieving some of the accumulated pressure inthe pressure accumulator 19. This avoids contaminating the rammingcomponent 3 with debris resulting from the firing of the firingmechanism 5 because the venting through vent 21 occurs separately fromthe venting through vent 23 of the ramming component 3 of the rammersystem 1. Thus, pressurized gaseous matter from the compressible gas 60and excess actuating fluid 22 is prevented from entering the rammingcomponent 3.

The actuating fluid 22 is driven from the pressure accumulator 19through an opening leading to a tube 17, which is configured narrowerthan the pressure accumulator 19, thereby creating a zone of increasedpressure within the tube 17 compared with the pressure accumulator 19.That is, the height of the tube 17 (and opening leading to the tube 17)is smaller than the height of the pressure accumulator 19.

The pressure in the tube 17 is further controlled by a valve 26connected to the tube 17. The actuating fluid 22, upon exiting the endof the tube 17, enters a rammer chamber 15 and engages a rammer 28. Therammer 28 is generally configured in an elongated “H” or rotated “I”configuration, however those skilled in the art would readily understandincorporating any functional configuration for the rammer 28.

Preferably, the rammer 28 comprises a pair of generally uprightcylindrical ends 38, 39 connected by a cylindrical rammer piston 35therebetween. A first surface 11 of a first upright end 38 contacts theactuating fluid 22 which exits the tube 17. A second surface 13 of thefirst upright end 38, which is on an opposite side of the first uprightend 38 from the first surface 11, engages a pair of bias elements 30such as springs which could be further embodied as pneumatic recoverysprings or hydro springs.

The bias elements 30 are positioned between the second surface 13 of thefirst upright end 38 of the rammer 28 and the back wall 9 of the rammerchamber 15. The rammer chamber 15 further comprises a vent 23 connectingto a valve 32 to help release accumulated pressure within the rammerchamber 15 caused by the pressure exerted on the rammer 28 by theactuating fluid 22. However, the vent 23 is not utilized or is notconfigured in the rammer chamber 15 at all if the bias elements 30 areembodied as pneumatic recovery springs or hydro springs.

An opening is configured in the outer casing 24 of the rammer chamber 15configured for allowing the rammer piston 35 to translate back andforth. Additionally, dust seals 8 are positioned on the back end 7 ofthe rammer chamber 15 such that the dust seals 8 are configured aroundthe rammer piston 35. Moreover, a portion of the rammer piston 35 alongwith the second upright end 39 of the rammer 28 is located outside therammer chamber 15. The second upright end 39 engages an artilleryprojectile or propellant charge 34 set on a loading tray 36.

FIG. 2 illustrates a second embodiment of an open cycle rammer assembly10 with the direct action of propellant gases. The rammer assembly 10 issimilarly configured to the open cycle rammer system 1 shown in FIG. 1,and as such like reference numerals in FIGS. 1 and 2 correspond to likecomponents in both schematics. Generally, the rammer assembly 10comprises an outer casing 24 which houses several sub-components. Thesesub-components include a firing mechanism 5, which is preferablyembodied as a primer, spark, or percussion or electric initiation-firingpin or probe.

The firing mechanism 5 connects to a breech closure 12, which ispreferably embodied as a horizontally guided sliding wedge. The breechclosure 12 connects to a first side of an actuator component 14 embodiedas a combustion chamber, a propellant cartridge, or a pressure vessel.On a second side of the actuator component 14 the rammer assembly 10includes a pressure accumulator 19 which holds the actuating fluid 22. Avent 21 connecting to a valve 20 is connected to the pressureaccumulator 19 to help release accumulated pressure (caused by actuationof the actuating fluid 22 upon firing of the firing mechanism 5) withinthe pressure accumulator 19.

The actuating fluid 22 which may be embodied as a propellant gas islocated in the pressure accumulator 19. The actuating fluid 22 is drivenfrom the pressure accumulator 19 and into a tube 17, which is configurednarrower than the pressure accumulator 19, thereby creating a zone ofincreased pressure within the tube 17 compared with the pressureaccumulator 19. One difference between the open cycle rammer assembly 10shown in FIG. 2 and the open cycle rammer system 1 shown in FIG. 1 isthat the rammer assembly 10 further comprises an optional particulatefilter 37 positioned in the tube 17, wherein the particulate filter 37may include a removable and replaceable filter having a porousthrottling medium 27 that filters particulates in the actuating fluid22. For gas generator grains that produce debris, the particulate filter37 is particularly useful for preventing the debris from clogging theramming component 3.

The pressure in the tube 17 is further controlled by a valve 26connected to the tube 17. The actuating fluid 22 upon exiting the end ofthe tube 17 enters the rammer chamber 15 and engages a rammer 28. Theremaining components of rammer assembly 10 are identical to similarcomponents in rammer system 1 as described above.

FIG. 3 illustrates a third embodiment of the invention which shows anopen cycle rammer system 25. The rammer system 25 is similarlyconfigured to the open cycle rammer system 1 shown in FIG. 1 and therammer assembly shown in FIG. 2, and as such like reference numerals inFIGS. 1, 2, and 3 correspond to like components in each schematic. Theprincipal difference between the third embodiment and each of the firstand second embodiments is that the third embodiment does not include atube 17, but rather the pressure accumulator 19 effectively joins withthe rammer chamber 15 (as such rammer chamber 15 is not specificallylabeled in FIG. 3).

FIGS. 4 through 7 illustrate successive stages of operation of a rammersystem 31 according to a fourth embodiment of the invention, whichutilizes a regeneration piston 48 to regenerate the actuating fluid 22.Regeneration is accomplished through action of the regeneration piston48 driven by the recoil motion of the recoiling parts (gun tube, breech,and cradle, collectively, the recoil mass 50) compressing the actuatingfluid 22 vented from the rammer chamber 15 in retraction of the rammerpiston 35. Generally, as shown in FIG. 4, high pressured gas 60 entersthe pressure accumulator 19 from the actuator component 14 via a checkvalve 33 that separates the actuator component 14 from the pressureaccumulator 19. The rammer system 31 further includes a second checkvalve 40 configured in the inner wall of the pressure accumulator 19,which connects to a regeneration cylinder 42 via a regeneration cylinderexit tube 41. The check valve 40 shown in FIG. 4 is closed to preventthe actuating fluid 22 from entering the regeneration cylinder exit tube41.

The regeneration cylinder 42 further comprises an inner chamber 43 thathouses a regeneration piston 48. The regeneration piston 48 is generally“T” shaped, although any functional configuration could be used.Preferably, the regeneration piston 48 is configured with a generallyupright cylindrical end 46, which comprises a first surface 51 and asecond surface 49, which is on an opposite side of the uprightcylindrical end 46 from the first surface 51. The second surface 49engages a pair of bias elements 47 such as springs which could befurther embodied as pneumatic recovery springs or hydro springs. Thebias elements 47 are positioned between the second surface 49 of theupright cylindrical end 46 and the inner back wall 52 of theregeneration cylinder 42. Furthermore, a regeneration cylinder entrytube 44 comprising a valve 45 is positioned between the regenerationcylinder 42 and the rammer chamber 15.

Next, as illustrated in FIG. 5, the check valve 33 connecting theactuator component 14 with the pressure accumulator 19 is closed as isthe check valve 40 connecting the pressure accumulator 19 to theregeneration cylinder exit tube 41. The high pressure gas 60 pushes thepiston 18, which then pushes the actuating fluid 22 through the tube 17and into the rammer chamber 15 with the valve 26 opened to accommodatethe entry of the actuating fluid 22 into the rammer chamber 15. As theactuating fluid 22 enters the rammer chamber 15 it engages the firstsurface 11 of the rammer 28, which actuates the rammer piston 35 causingthe rammer piston 35 to translate toward and engage the projectile orpropellant charge 34 on the loading tray 36. As the rammer piston 35moves toward the projectile or propellant charge 34, the bias elements30 are compressed between the second surface 13 of the first upright end38 of the rammer 28 and the back wall 9 of the rammer chamber 15. Someof the actuating fluid 22 may enter the regeneration cylinder entry tube44. However, the valve 45 in the regeneration cylinder entry tube 44 isclosed thereby preventing the actuating fluid 22 from entering the innerchamber 43 of the regeneration cylinder 42.

Then, as depicted in FIG. 6, after the second upright end 39 of therammer 28 engages an artillery projectile or propellant charge 34, thebias elements 30 are released from their compressed state, therebytranslating the rammer piston 35 towards tube 17, which pushes theactuating fluid 22 into the inner chamber 43 of the regenerationcylinder 42. In other words, the rammer piston 35 retracts, therebydisplacing the actuating fluid 22 from the rammer chamber 15 into theregeneration cylinder 42. This is further accomplished by closing thevalve 26 in tube 17 and opening the valve 45 in the regenerationcylinder entry tube 44. That is, the valve 26 between the pressureaccumulator 19 and rammer chamber 15 is closed to prevent the actuatingfluid 22 from re-entering the pressure accumulator 19, and the valve 45from the rammer chamber 15 to the regeneration cylinder 42 is opened.Some of the actuating fluid 22 may enter the regeneration cylinder exittube 41. However, with the check valve 40 closed, the actuating fluid 22is prevented from entering the pressure accumulator 19. Furthermore, asthe actuating fluid 22 enters the inner chamber 43 of the regenerationcylinder 42, the actuating fluid 22 engages the first surface 51 of theupright cylindrical end 46 of the regeneration piston 48, therebycausing the regeneration piston 48 to translate in a direction towardsthe recoil mass 50, and further causing compression of the bias elements47 positioned between the second surface 49 of the upright cylindricalend 46 and the inner back wall 52 of the regeneration cylinder 42.

FIG. 7 illustrates the next sequence in the regeneration process,wherein recoil motion of the gun/cannon (not shown) causes the recoilmass 50 to force the regeneration piston 48 in a direction opposite tothe recoil mass 50, thereby releasing the compressed bias elements 47and pushing the actuating fluid 22 into the regeneration cylinder exittube 41. As such, when the pressure is sufficiently high, the actuatingfluid 22 is forced from the regeneration cylinder 42 back into thepressure accumulator 19 via the open check valve 40. The valve 45 in theregeneration cylinder entry tube 44 as well as the valve 26 in the tube17 is closed to prevent the actuating fluid from re-entering the rammerchamber 15. The regeneration process is generally complete at thispoint, and the rammer system 31 is now set to begin the ramming processagain (i.e., the sequence repeats as illustrated in FIGS. 4-7).

FIGS. 8( a) through 8(e) illustrate various embodiments of the actuatorcomponent 14, wherein reference to like numerals correspond to likeelements. According to a first embodiment illustrated in FIG. 8( a), theactuator component 14 comprises a casing 140 comprising a combustionchamber 142 configured for housing a solid propellant 141, such asgranulated or propellant grain. Additionally, a pair of flanges 146forms opposite ends of a front wall 143 of the casing 140. The frontwall 143 connects to the back portion of the breech closure 12illustrated in FIGS. 1 and 2. As such, the firing mechanism 5 is formedin the front wall 143, wherein the firing mechanism 5 is preferablyembodied as an electric or percussion primer configured for initiating acharge or spark to the solid propellant 141.

Furthermore, configured in the casing 140 opposite the front wall 143 isa plurality of holes 148, which lead to a perforated disc 150 to retaina high pressure to provide for stable burning of the solid propellant141. The holes 148 may also be embodied as a porous material. Theperforated disc 150 may be a rupture disc and can be configured in anygeometry that retains gas pressure but that also allows for free ventingof reduced pressure gas. A pressure reservoir 153 is positioned adjacentto the perforated disc 150, which then connects to a particulate filter152 that connects to a portion of the casing 140.

In a second embodiment shown in FIG. 8( b), the actuator component 14comprises a casing 140 comprising a combustion chamber 142 configuredfor housing a liquid propellant 145, such as a hydroxyl ammonium nitrate(HAN) slurry in water. As with the first embodiment, a pair of flanges146 form opposite ends of a front wall 143 of the casing 140 with afiring mechanism 5 also formed in the front wall 143. Configured in thecasing 140 opposite the front wall 143 is a rupture disc 154, whichleads to a pressure reservoir 156, which is preferably embodied as aperforated cylinder configured to retain a high pressure to allow forstable reaction of the liquid propellant 145. A plurality of holes 160is disposed on diametrically opposite sides of the pressure reservoir156, which lead to cylindrical rupture barriers 158, which then lead toa pneumatic chamber 168. A particulate filter 162 is further attached tothe casing 140 and positioned spaced apart from the pressure reservoir156 with the pneumatic chamber 168 positioned therebetween.

FIG. 8( c) illustrates a third embodiment of the actuator component 14.Structurally, the third embodiment is similar to the second embodimentexcept that in lieu of a particulate filter 162 as provided in thesecond embodiment, the third embodiment includes a slidably mountedclosure wedge 164 serving as a mechanical membrane barrier for theactuator component 14 to prevent dirt from entering the actuatorcomponent 14. Another difference between the third embodiment and thesecond embodiment is that in the third embodiment the propellant is amonopropellant mixture 147 comprising a liquid monopropellant such ashydrogen peroxide or hydrazine plus a decomposition catalyst. Themonopropellant mixture 147 (liquid monopropellant and catalyst) areseparated by barrier capsules 165 ruptured by the pressure of the firingmechanism 5.

The geometry of the monopropellant mixture 147 is dependent on thechoice of materials. For example, H₂O₂ may be confined in a barriercapsule 165 next to the firing mechanism 5. Once the firing mechanism 5ruptures the barrier capsule 165, the H₂O₂ floods the combustion chamber142 comprising granulated manganese dioxide or potassium permanganate.The concentrated H₂O₂ then decomposes into steam. Thereafter, therupture disc 154 breaks allowing the gas to flood the pressure reservoir156.

In a fourth embodiment, as illustrated in FIG. 8( d), the actuatorcomponent 14 is structurally similar to the third embodiment, except thepropellant comprises a hybrid propellant 149 such as an augmentation ofgas volume/pressure by a phase change, or a burning flammablegas/oxidizer. Use of a phase change material may allow a greaterincrease in volume of gas from the generator component 2 by tradingtemperature of the fluid for an increase in gas volume by flashing aliquid into a gas. An example is microspheres or microbeads of waterturning into steam. This reduces the temperature of the pressurizing gasfrom the gas generator component 2 but increases the volume and pressureof the gas by transforming a low volume liquid into a high volume gas.Another example is liquid H₂O₂ decomposing into H₂O steam and O₂. The O₂can then be used to react with a fuel releasing heat and hence increasepressure for a given weight of reactant.

Thus, in the example above the gas generating material may include asolid propellant mixed with a first capsule or microbead 166 comprisinga phase change material such as water or fuel such as hydrocarbon orplastic, and is mixed with a second capsule or microbead 167 comprisingan oxidizer. In the latter case, the goal is deflagration (burning)rather than detonation, which is an explosive process involving a shockwave. If an engine detonates (pings) it loses power, whereas steadyburning produces the most power. The pressurizing fluid passes throughthe rupture disc 154 by rupturing it, and by going through the closurewedge 164 because the wedge material is porous with hole sizes too smallfor dirt.

According to a fifth embodiment, the actuator component 14, as shown inFIG. 8( e), comprises a casing 140 that includes a combustion chamber142 configured for housing a gas propellant 151, which is under highpressure. As with the previous embodiments, a pair of flanges 146 formsopposite ends of a front wall 143 of the casing 140. In the fifthembodiment, a pair of firing mechanisms 5, 144 is formed on oppositewalls (front wall 143 and back wall 155) of the casing 140, wherein thefiring mechanisms 5, 144 are preferably embodied as electric orpercussion primers configured for initiating a charge to the gaspropellant 151. A charge tube 169 further connects the two firingmechanisms 5 to one another. Additionally, the firing mechanisms 5, 144in the fifth embodiment are configured for allowing venting of the highpressure gas resulting from the charge to the gas propellant 151. Theventing occurs through gaps (not shown) created in locations occupied bythe firing mechanism 5, 144. That is, the initiation of the firingmechanisms 5, 144 essentially blows out the firing mechanism 5, 144thereby creating gaps (not shown) in the casing 140 to allow forventing.

During operation, the gun crew inserts an initializing actuatorcomponent 14 such as a gas generating cartridge into position and closesthe breech closure 12. The actuator component 14 may comprise blackpowder, smokeless powder, a gas generating compound such as solid rocketfuel, a monopropellant such as hydrazine or hydrogen peroxide, or evencompressed gas. If any combustible gas generating material is includedin the actuator component 14, then the gas generating material isignited by a percussion or electrical squib using the firing mechanism5. If the actuator component 14 includes a monopropellant, then themonopropellant is released onto a catalyzing bed by a squib activatedperforated disc 150 (shown in FIG. 8( a)) such as a rupture disc orpower or manual valve. If the combustible material requires highpressure for stable burning, such as a liquid propellant such ashydroxyl ammonium nitrate (HAN) or gunpowder, the actuator component 14may be embodied as a small combustion chamber 142 sealed off by aperforated disc 150 such as a rupture disc activated by pressure, whichcovers a throttling hole or holes 148 as shown in FIG. 8( a).

When the crew is ready to ram the projectile or propellant charge 34they place the projectile or propellant charge 34 in the loading tray 36by mechanical or manual means, and then open the valve 26 from thepressure accumulator 19 to the rammer chamber 15, allowing the actuatingfluid 22 to compress the rammer piston 35, which pushes the projectileor propellant charge 34 into the gun/cannon chamber (not shown).

Once the projectile or propellant charge 34 is properly seated, therammer piston 35 retracts. The retracting rammer piston 35 pushes theactuating fluid 22 out of the rammer chamber 15 which further actuatesthe rammer piston 35. The actuating fluid 22 may be vented to atmosphereor vented to the regeneration cylinder 42 as shown in FIGS. 4 through 7.Venting to atmosphere is the lowest weight option, but the actuatingfluid 22 must then be replenished after each shot.

If the round is separately loaded, the projectile or propellant charge34 is placed in the loading tray 36 and the actuating fluid 22 isallowed to act on the rammer piston 35 again, ramming the projectile orpropellant charge 34 into the chamber (not shown). The rammer piston 35is retracted and the gun breech (not shown) is closed. When ready, thecrew fires the gun/cannon (not shown), which recoils within its cradleshown as recoil mass 50. The recoil motion may actuate the regenerationpiston 48 to compress the actuating fluid 22 back into the pressureaccumulator 19 (regeneration) as shown in FIGS. 4 through 7. If theactuating fluid 22 is air, it may be vented and a new supply of air isthen compressed into the pressure accumulator 19.

FIG. 9 (in accordance with the embodiments and components shown in FIGS.1 though 8(e)) illustrates a method of ramming an artillery projectileor propellant charge 34 according to an aspect of the invention, whereinthe method comprises triggering (201) combustion of a combustiblepropellant 141, 145, 147, 149, 151 into an actuating fluid 22. Next, themethod involves pressurizing (203) the actuating fluid 22 in an actuatorcomponent (such as a pressure vessel) 14 and controlling (205) a flow ofthe pressurized fluid 22 in a pressure accumulator 19. Thereafter, theinvention involves ramming (207) any of an artillery projectile andpropellant charge 34 using a rammer 28 driven by power generated by thepressurized fluid 22, and regenerating (209) pressure in the pressureaccumulator 19 using recoil motion of the rammer 28.

The triggering (201) occurs using a firing mechanism 5 comprising any ofa catalyst, spark-generating mechanism, and a percussion or electricinitiation-firing pin or probe. Additionally, the combustible propellantcomprises any of a solid propellant 141, a liquid propellant 145, a gaspropellant 151, and a combination thereof (hybrid propellant) 149.Alternatively, the combustible propellant comprises a monopropellantmixture 147 comprising a liquid monopropellant and a catalyst.

Generally, the invention uses a gas generator component 2 configured forpowering a ramming component 3 of an artillery rammer system 1. Morespecifically, the gas generator component 2 produces a source of highpressure gas, which may, if desired, act through a pressure accumulator19 on a rammer 28 to effectuate the ramming sequence. For gas generatorgrains that produce debris, particulate filters 37 may be incorporatedif needed. The gas generator component 2 may use either pyrotechnics orpropellants 141, 145, 149, or produce either gas (gas propellant 151)alone or gas and steam through the decomposition of a monopropellantmixture 147 such as hydrogen peroxide or hydrazine.

Moreover, gas generation by artillery propellants 141, 145, 147, 149,151 require high pressure for stable burning. The required pressure canbe attained for small quantities of propellant 141, 145, 147, 149, 151through use of the high-low process. In this process, used for examplein a 40 mm grenade launcher, a quantity of propellant 141, 145, 147,149, 151 is burned in a low volume, thick walled actuator component 14,which is vented through a small hole 148 that is closed by a rupture orperforated disc 150. The perforated disc 150 breaks and vents the gasesonce the proper pressure has been reached.

Several embodiments for the lightweight actuator component 14 exist. Thepropellants can be either single, double, or triple base solidpropellants 141, or liquid propellants 145 being developed for the nextgeneration of artillery systems. The liquid propellant systems usematerials such as HAN (hydroxyl ammonium nitrate in water).

According to the embodiments of the invention, the rammer system 1includes lightweight components actuated by gases produced by apyrotechnic device such as a cake of a grain of propellant 141, a liquidpropellant 145, a quantity of a monopropellant mixture 147, a gaspropellant 151, or a hybrid propellant 149. The actuator component 14 isembodied as a pneumatic device and is open cycle. Advantages of theembodiments of the invention over conventional rammer systems are thereduced weight, reduced cost, and overall simplicity in design affordedby the embodiments of the invention.

Again, artillery with auxiliary power such as the South African G-5 maybe used to power the rammers. The former Soviet 2A36 and 2A65 towedartillery pieces use a rammer. The rammer and breech of the 2A36 areoperated from a hydraulic reservoir charged by recoil, but until thefirst shot, the rammer for the 2A36 is initially manually operated. Therammer for the 2A65 uses a spring assisted mechanism. As mentioned,these types of towed artillery pieces are extremely heavy, and may notbe suitable for air transport. With regard to the reduced weightafforded by the embodiments of the invention, the actuator component 14and pressure accumulator 19 are lighter in weight than an auxiliarypower unit (APU), a hydraulic pump, and an accumulator as used inconventional ramming systems such as the man-powered South African G-5,or a hydropneumatic accumulator found in the conventional former Soviet2A36 system, or the spring-assisted components of the conventionalformer Soviet 2A65 system.

Moreover, the consumable propellants 141, 145, 147, 149, 151 are alsolightweight, and the nontoxic monopropellant mixture 147 exhausts steamand oxygen from the decomposition of hydrogen peroxide or gases fromliquid artillery propellants, which then may be vented at low pressure.According to the embodiments of the invention, regeneration savesconsumables propellants, and using a gas generator on each loading savesweight mounted on the gun at the expense of consumables propellants.

The embodiments of the invention provide a rammer system 1 that issufficiently lightweight to be dismountable and transported separatelyfrom other artillery pieces to save weight when sling loading, ifnecessary. Because there are no hydraulic reservoirs or motors on therammer system 1, the rammer system 1 could slip over studs on thecarriage of the gun, perhaps engaging the recoiling mass by a pad, couldbe removable, and could be lifted by as few as two crewmen.

Other advantages afforded by the embodiments of the invention areincreased speed, reduced fatigue, reduced heat stress when wearingchemical protective gear, especially overgarments, reduced personnelrequirements, and increased safety. With regard to speed, the projectileor propellant charge 34 may be placed on the loading tray 36 andimmediately rammed. The process and time for fitting a ram staff on theitem to be rammed, getting the crew ready, and ramming, are reduced tothe setting of a control.

With regard to reduced fatigue, a 155 mm projectile M107 High Explosiveweighs approximately 95 pounds. Ramming a 95 pound projectile up an 85degree slope (maximum elevation) hard enough to seat the projectile inthe rifling requires significant effort. The propellant (powder) chargeis of comparable weight. The OF-29 unitary HE projectile for the 2A36152 mm towed artillery piece is 101 lbs (46 kg). The charge is 76.6 lbs(34.8 kg). For those armies with heavier pieces of artillery thecorresponding weights are greater. Thus, because there is already muchphysical exertion required to ram a projectile, the reduced weightprovided by the embodiments of the invention allows for a reduction ofthe fatigue of crewmen.

With regard to reduced heat stress in chemical protective gear. Presentwestern chemical protective gear is based on a layered ensemble oftreated cloth and a charcoal impregnated intermediate layer. Theselayers reduce the effectiveness of perspiration in cooling the body. Ina desert climate the effect of heat is worse. Adding heavy exertionmakes the heat load difficult to cope with. Eastern designed chemicalprotective equipment is based on an impermeable rubber suit thatcompletely blocks ventilation. Reduction of muscular activity to aminimum is highly desirable in both cases. As such, the reduced weightprovided by the embodiments of the invention allows for this reductionof muscular activity.

With regard to reduced personnel requirements, the reduced weightprovided by the embodiments of the invention allows for fewer number ofcrewmen required to handle the ramming of a projectile compared toconventional systems. With regard to increased safety, the variousembodiments of the invention allow for increased safety of the rammingof the projectile or propellant charge. Moreover, reduction in thenumber of personnel required to handle the ramming as well as some ofthe other advantages described above further increases the overallsafety provided by the embodiments of the invention.

The foregoing description of the specific embodiments will so fullyreveal the general nature of the invention that others can, by applyingcurrent knowledge, readily modify and/or adapt for various applicationssuch specific embodiments without departing from the generic concept,and, therefore, such adaptations and modifications should and areintended to be comprehended within the meaning and range of equivalentsof the disclosed embodiments. It is to be understood that thephraseology or terminology employed herein is for the purpose ofdescription and not of limitation. Therefore, while the invention hasbeen described in terms of preferred embodiments, those skilled in theart will recognize that the embodiments of the invention can bepracticed with modification within the spirit and scope of the appendedclaims.

1. A rammer system for engaging an artillery projectile or propellantcharge, said rammer system comprising: an internal combustion generatorcomprising: a first firing mechanism; an actuator driven by said firingmechanism, wherein said actuator comprises a propellant combustible intoa pressurized fluid; and a pressure accumulator connected to saidactuator, wherein said pressure accumulator controllably releases saidpressurized fluid; and a ramming component for engaging an artilleryprojectile or propellant charge connected to said internal combustiongenerator and powered by said pressurized fluid
 2. The system of claim1, further comprising means for regenerating pressure in said pressureaccumulator actuated by recoil motion of said ramming component.
 3. Thesystem of claim 1, wherein said first firing mechanism comprises any ofa catalyst, a spark-generating mechanism, and a percussion or electricinitiation-firing pin or probe.
 4. The system of claim 1, wherein saidactuator comprises: a combustion chamber configured for allowing saidpropellant to combust upon actuation from said first firing mechanism;and a first rupture disc connected to said combustion chamber.
 5. Thesystem of claim 4, wherein said actuator further comprises: at least onehole configured in said actuator and positioned between said combustionchamber and said first rupture disc; a pressure reservoir adjacent tosaid first rupture disc; and a particulate filter adjacent to saidpressure reservoir.
 6. The system of claim 4, wherein said actuatorfurther comprises: a pressure reservoir connected to said first rupturedisc; a second rupture disc; a plurality of holes configured in saidactuator and positioned between said pressure reservoir and said secondrupture disc; and a pneumatic chamber adjacent to said second rupturedisc.
 7. The system of claim 6, wherein said actuator further comprisesa slidably mounted closure wedge connected to said pneumatic chamber. 8.The system of claim 6, wherein said actuator further comprises aparticulate filter adjacent to said pneumatic chamber.
 9. The system ofclaim 1, wherein said actuator comprises: a combustion chamberconfigured for allowing said propellant to combust upon actuation fromsaid first firing mechanism; a second firing mechanism; and a chargetube connecting said first firing mechanism to said second firingmechanism.
 10. The system of claim 1, wherein said propellant comprisesany of a solid propellant, a liquid propellant, a fluid propellant, anda combination thereof.
 11. The system of claim 1, wherein saidpropellant comprises a liquid monopropellant and a catalyst.
 12. Thesystem of claim 1, wherein said pressure accumulator comprises: a firstorifice connected to said actuator; a piston; a pressure release valve;a second orifice separated from said first orifice by said piston,wherein said second orifice being configured to have a height smallerthan a height of said pressure accumulator; a tube portion connected tosaid second orifice; and a fluid release valve disposed in said tubeportion.
 13. The system of claim 12, further comprising a particulatefilter disposed in said tube portion.
 14. The system of claim 12,wherein said ramming component comprises: a rammer chamber connected tosaid tube portion; a rammer piston enclosed in a portion of said rammerchamber; at least one bias member connecting said rammer piston to saidrammer chamber; a pressure vent disposed in said rammer chamber; and anopening in said rammer chamber configured for allowing translation ofsaid rammer piston therebetween.
 15. The system of claim 14, whereinsaid ramming component further comprises a seal configured in saidopening and positioned proximate to said rammer piston.
 16. The systemof claim 14, wherein said rammer piston comprises a generally elongatedcylindrical shaft portion and a pair of generally cylindrical endportions positioned on opposite ends of said shaft portion.
 17. Anartillery ramming assembly comprising: a firing mechanism; an actuatorconnected to said firing mechanism, wherein said actuator comprises apropellant decomposable into a pressurized fluid; a pressure accumulatorconnected to said actuator, wherein said pressure accumulator isconfigured for controlling a flow of said pressurized fluid; and arammer for engaging an artillery projectile or propellant chareconnected to said pressure accumulator and powered by said pressurizedfluid.
 18. The assembly of claim 17, further comprising means forregenerating pressure in said pressure accumulator actuated by recoilmotion of said rammer.
 19. The assembly of claim 17, wherein said firingmechanism comprises any of a catalyst, a spark-generating mechanism, anda percussion or electric initiation-firing pin or probe.
 20. Theassembly of claim 17, wherein said actuator comprises: a combustionchamber configured for allowing said propellant to combust uponactuation from said firing mechanism; and a first rupture disc connectedsaid combustion chamber.
 21. The assembly of claim 20, wherein saidactuator further comprises: at least one hole configured in saidactuator and positioned between said combustion chamber and said firstrupture disc; a pressure reservoir adjacent to said first rupture disc;and a particulate filter adjacent to said pressure reservoir.
 22. Theassembly of claim 20, wherein said actuator further comprises: apressure reservoir connected to said first rupture disc; a secondrupture disc; a plurality of holes configured in said actuator andpositioned between said pressure reservoir and said second rupture disc;and a pneumatic chamber adjacent to said second rupture disc.
 23. Theassembly of claim 22, wherein said actuator further comprises a slidablymounted closure wedge connected to said pneumatic chamber.
 24. Theassembly of claim 22, wherein said actuator further comprises aparticulate filter adjacent to said pneumatic chamber.
 25. The assemblyof claim 17, wherein said actuator comprises: a combustion chamberconfigured for allowing said propellant to combust upon actuation fromsaid firing mechanism; a charge-triggering mechanism; and a charge tubeconnecting said firing mechanism to said charge-triggering mechanism.26. The assembly of claim 17, wherein said propellant comprises any of asolid propellant, a liquid propellant, a fluid propellant, and acombination thereof.
 27. The assembly of claim 17, wherein saidpropellant comprises a monopropellant comprising a liquid monopropellantand a catalyst.
 28. The assembly of claim 17, wherein said pressureaccumulator comprises: a first orifice connected to said actuator; apiston; a pressure release valve; a second orifice separated from saidfirst orifice by said piston, wherein said second orifice beingconfigured to have a height smaller than a height of said pressureaccumulator; a tube portion connected to said second orifice; and afluid release valve disposed in said tube portion.
 29. The assembly ofclaim 28, further comprising a particulate filter disposed in said tubeportion.
 30. The assembly of claim 28, wherein said rammer comprises: arammer chamber connected to said tube portion; a rammer piston enclosedin a portion of said rammer chamber; at least one bias member connectingsaid rammer piston to said rammer chamber; a pressure vent disposed insaid rammer chamber; and an opening in said rammer chamber configuredfor allowing translation of said rammer piston therebetween.
 31. Theassembly of claim 30, wherein said rammer further comprises a sealconfigured in said opening and positioned proximate to said rammerpiston.
 32. The assembly of claim 30, wherein said rammer pistoncomprises a generally elongated cylindrical shaft portion and a pair ofgenerally cylindrical end portions positioned on opposite ends of saidshaft portion.
 33. An artillery ramming system comprising: means fortriggering combustion of a combustible propellant into a fluid; meansfor pressurizing said fluid; means for controlling a flow of thepressurized fluid; means, powered by said pressurized fluid, for rammingany of an artillery projectile and propellant charge; and means,actuated by recoil motion of said means for ramming, for regeneratingpressure in said artillery ramming system.
 34. A method of ramming anartillery or propellant charge, said method comprising: triggeringcombustion of a combustible propellant into a fluid; pressurizing saidfluid into a pressure vessel; controlling a flow of the pressurizedfluid in a pressure accumulator; ramming any of an artillery projectileand propellant charge using a rammer driven by power generated by saidpressurized fluid; and regenerating pressure in said pressureaccumulator using recoil motion of said rammer.
 35. The method of claim34, wherein said triggering occurs using a firing mechanism comprisingany of a catalyst, a spark-generating mechanism, and a percussion orelectric initiation-firing pin or probe.
 36. The method of claim 34,wherein said triggering, said combustible propellant comprises any of asolid propellant, a liquid propellant, a fluid propellant, and acombination thereof
 37. The method of claim 34, wherein in saidtriggering, said combustible propellant comprises a liquidmonopropellant and a catalyst.